Discharge device for aircraft

ABSTRACT

The present invention provides a discharge device for an aircraft, in which an aerosol container can easily be attached to an airframe and an operation for exchanging the aerosol container can be performed easily, resulting in a high degree of safety. A discharge device for an aircraft, to which an aerosol container can be attached and which discharges contents of the aerosol container when attached to an aircraft, is mounted on an airframe of the aircraft in a state where the aerosol container is housed in a housing member.

TECHNICAL FIELD

The present invention relates to a discharge device for an aircraft suchas an unmanned aircraft, which discharges a liquid, a gas, air, a sound(a horn), or the like from the aircraft, and more particularly to adischarge device having an aerosol container that discharges contentsthereof in response to gas pressure.

BACKGROUND ART

A bee extermination device such as that described in Patent Literature1, for example, is known in the prior art as a discharge device for anunmanned aircraft that uses this type of aerosol container.

More specifically, a chemical agent supply unit for supplying a chemicalagent into a bee's nest is provided in the interior of an airframe, andan aerosol container is attached to the chemical agent supply unit as aninjection tool.

CITATION LIST Patent Literature

-   Patent Literature 1: Japanese Patent Application Publication No.    2017-104063

SUMMARY OF INVENTION Technical Problem

In the device of Patent Literature 1, however, the aerosol container isattached in the interior of the airframe, and therefore the airframemust be significantly modified in order to fit the aerosol container.Aerosol containers come in various sizes, such as diameters and heights,and therefore, when the size does not fit, further modifications arenecessary. Moreover, the shape and size of the airframe are also limitedby the need to install the aerosol container.

Furthermore, when exchanging the aerosol container, it is necessary toremove the aerosol container from the interior of the airframe and housea new aerosol container therein while avoiding the rotor, and thereforethe exchange operation is complicated.

To solve these problems, the aerosol container may be attached to theexterior of the airframe using a clamp member, but in the event of amulticopter crash, a direct impact may be exerted on the aerosolcontainer, causing perforation and outflow of contents.

Further, the aerosol container must be structured safely so that whenthe aerosol container is gripped, an aerosol container can does not falloff, and in this case, it may be necessary to perform special shapingprocessing on the aerosol container, select a special surface materialtherefor, and so on while also ensuring that the aerosol container caneasily be exchanged.

The present invention has been designed to solve the problems in theprior art, described above, and an object thereof is to provide adischarge device for an aircraft, in which an aerosol container caneasily be attached to an airframe and an exchange operation can beperformed easily, resulting in a high degree of safety.

Solution to Problem

To achieve the object described above, a discharge device according tothe present invention is a discharge device for an aircraft, to which anaerosol container can be attached and which discharges contents of theaerosol container when attached to the aircraft,

wherein the discharge device is mounted on an airframe of the aircraftin a state where the aerosol container is housed inside a housingmember.

According to the present invention, the aerosol container is attached tothe airframe of the aircraft via the housing member, and therefore theaerosol container can be attached to the airframe of the aircraftwithout modifying the interior configuration of the airframe.

In other words, it is only necessary to prepare a housing membercorresponding to the diameter and size of the aerosol container and notnecessary to significantly modify the airframe, and therefore a highdegree of convenience is achieved. Further, a mounting method suited tothe shape of the airframe can be adopted, and therefore a high degree ofversatility is achieved.

Furthermore, the aerosol container can easily be exchanged simply byattaching the aerosol container to the airframe together with thehousing member or attaching the aerosol container to the housing membermounted on the airframe, and therefore an exchange operation is easy.

Moreover, the aerosol container is protected from impacts by the housingmember, and therefore a high degree of safety is achieved.

In particular, by increasing the degree of sealing of the housingmember, the degree to which a container main body is directly exposed tothe external environment can be reduced, and as a result, variation ininternal pressure due to temperature variation can be suppressed.

The present invention is configured as follows.

1. A discharge drive unit is provided to discharge contents from theaerosol container.

2. The discharge drive unit is configured to discharge the contents bymoving a container main body of the aerosol container so that a stemprojecting from the container main body is pressed into the containermain body.

By moving the aerosol container while housed in the housing member, anactuator-side position can be kept constant.

3. The discharge drive unit is provided in the housing member.

By providing the discharge drive unit in the housing member, anappropriate mechanism can be selected for the size, shape, and weight ofthe aerosol container, and as a result, an optimum structure can beprovided for the aerosol container.

4. The housing member and the airframe are provided with couplingportions that are coupled to each other.

By unifying the standard of the coupling portions, housing members foraerosol containers of different sizes and types can be exchanged.

5. The discharge drive unit is provided on the airframe side.

By providing the discharge drive unit on the airframe side, it is notnecessary to provide the discharge drive unit on the housing memberside, and therefore the configuration on the housing member side can besimplified, enabling a cost reduction.

6. A coupling portion by which the housing member is coupled to thedischarge drive unit is provided.

By coupling the housing member to the discharge drive unit, a couplingportion for coupling the housing member to the airframe is not required.

7. A control device for controlling the discharge drive unit is furtherprovided.

The control device may be provided separately from a control device ofthe aircraft or incorporated into the control device of the aircraft.When the control devices are provided separately, there is no need tomodify the control device of the aircraft, and attachment can besimplified.

8. The control device is provided on the airframe side.

By providing the control device on the airframe side, the control devicecan be integrated when exchanging the housing member.

9. The control device is provided on the housing member side.

By providing the control device on the housing member side, there is noneed to provide electrical contacts or the like on the couplingportions.

10. A communication device for operating the discharge drive unitremotely is further provided.

The communication device may likewise be provided separately from acommunication device of the aircraft or integrated with thecommunication device of the aircraft. When the communication devices areprovided separately, remote operations can be performed withoutmodifying the communication device of the aircraft.

11. A power supply for driving the discharge drive unit is provided.

By providing a dedicated power supply, excessive wear on the powersupply of the aircraft can be avoided.

12. The power supply is provided on the airframe side.

By providing the power supply on the airframe side, the power suppliescan be integrated when exchanging the housing member. Moreover, theconfiguration on the housing member side can be simplified.

13. The power supply is provided on the housing member side.

Thus, there is no need to provide electrical contacts or the like on thecoupling portions.

14. A power supply used to control flight of the aircraft is used as thepower supply for driving the discharge drive unit.

Thus, the power supply configuration can be simplified.

15. The discharge drive unit includes a driving mechanism thatdischarges the contents by fixing either a container main body of theaerosol container or a stem that projects from the container main bodyand moving the other so that the other is moved in a direction forpressing in the stem relative to the container main body.

Thus, the existing aerosol container can be used while attached to thehousing member.

16. The aerosol container is exchangeable relative to the housingmember.

Thus, it is possible to exchange only the aerosol container, andtherefore the housing member can be universalized.

17. The housing member includes a housing member main body in which theaerosol container is housed, and a lid body for opening and closing anopening portion provided in the housing member main body, and theaerosol container can be exchanged by opening the lid body in a statewhere the housing member main body is attached to the airframe.

Thus, the aerosol container can be exchanged easily.

18. The housing member main body is formed in a tubular shape extendingin a central axis direction of the aerosol container, and the openingportion and the lid body are provided on a head portion side and/or abottom portion side of the aerosol container.

Thus, the aerosol container can be exchanged even more easily.

19. The opening portion and the lid body are provided on the headportion side of the aerosol container, and the housing member isconfigured so as to open on the head portion side of the aerosolcontainer.

20. The opening portion and the lid body are provided on the bottomportion side of the aerosol container, and the housing member isconfigured so as to open on the bottom portion side of the aerosolcontainer.

21. The lid body includes the discharge drive unit and is configured soas to be detached from the housing member main body together with thedischarge drive unit.

22. The lid body is configured to be screwed to the housing member mainbody.

23. The lid body includes fixing means that is supported to be capableof rotating relative to the housing member main body via a hinge andthat couples and fixes the lid body in a closed position.

The lid body can be opened and closed easily.

24. The fixing means is a snap lock.

An operation to fix the lid body can be performed easily.

25. The lid body is engaged to the housing member main body by aplurality of fixing means.

A hinge is not necessary.

26. The aerosol container is integrated with the housing member so as tobe non-exchangeable.

By integrating the aerosol container, the exchange operation can beperformed easily. Further, mistakes when attaching the aerosol containercan be avoided, and therefore a high degree of safety is achieved.

27. The housing member includes a support portion that holds the aerosolcontainer by means of a structure having a distance from a wall surfaceof the housing member.

By employing a structure having a distance from a wall surface of thehousing member, thermal insulation can be realized by air or a layer ofinsulating material between the aerosol container and the housingmember.

Further, when the discharge device is dropped, the holding portionserves as a shock-absorbing mechanism, and therefore the impact on theaerosol container can be alleviated.

Advantageous Effects of Invention

According to the present invention, as described above, it is possibleto realize a discharge device for an aircraft, in which an aerosolcontainer can easily be attached to an airframe and an exchangeoperation can be performed easily, resulting in a high degree of safety.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a conceptual view of a discharge device for an aircraftaccording to a first embodiment of the present invention, wherein FIG.1(A) is a front view, FIG. 1(B) is a side view, and FIG. 1(C) is a viewshowing a state in which a housing member has been removed.

FIG. 2(A) is a sectional view taken in a right-angled direction to anaxis of a support portion of a sleeve shown in FIG. 1 , FIG. 2(B) is aview showing an example of a valve configuration of an aerosol containershown in FIG. 1 , FIG. 2(C) is a view showing an example in which apower supply of a flight control unit is used as a power supply, andFIG. 2(D) is a view showing an example configuration of couplingportions.

FIGS. 3(A) to 3(C) are views showing three methods employed by adischarge drive unit.

FIG. 4 is a view showing an example of a steering terminal and adischarge operation terminal.

FIG. 5 is a view showing an example in which an extension tube is usedin the discharge device for an aircraft of FIG. 1 , wherein FIG. 5(A) isa front view and FIG. 5(B) is an exploded front view showing a state inwhich the housing member has been removed.

FIG. 6 is a view showing modified example 1 of the first embodiment ofthe present invention, wherein FIG. 6(A) is a front view showing a statein which the sleeve has been removed from an airframe and FIG. 6(B) is afront view showing a state in which the sleeve is coupled to theairframe.

FIG. 7 is a view showing modified example 2 of the first embodiment ofthe present invention, wherein FIG. 7(A) is a front view showing a statein which the sleeve has been removed from the airframe and FIG. 7(B) isa front view showing a state in which the sleeve is coupled to theairframe.

FIG. 8 is a view showing modified example 3 of the first embodiment ofthe present invention, wherein FIG. 8(A) is a front view showing a statein which the sleeve has been removed from the airframe and FIG. 8(B) isa front view showing a state in which the sleeve is coupled to theairframe.

FIG. 9 is a view showing modified example 4 of the first embodiment ofthe present invention, wherein FIG. 9(A) is a front view showing a statein which the sleeve has been removed from the airframe and FIG. 9(B) isa front view showing a state in which the sleeve is coupled to theairframe.

FIG. 10 is a view showing modified example 5 of the first embodiment ofthe present invention, wherein FIG. 10(A) is a front view showing astate in which the sleeve has been removed from the airframe and FIG.10(B) is a front view showing a state in which the sleeve is coupled tothe airframe.

FIG. 11 is a view showing modified example 6 of the first embodiment ofthe present invention, wherein FIG. 11(A) is a front view showing astate in which the sleeve has been removed from the airframe and FIG.11(B) is a front view showing a state in which the sleeve is coupled tothe airframe.

FIGS. 12(A) to 12(C) are views showing other arrangement configurationsof the housing member of FIG. 1 .

FIGS. 13(A) to 13(C) are views showing examples of mounting layouts ofthe housing member.

FIGS. 14(A) to 14(C) are views showing layouts in which the housingmember is mounted on the airframe via an arm.

FIG. 15(A) is a view showing another example configuration of thedischarge drive unit, and FIG. 15(B) is a view showing a further exampleconfiguration of the discharge drive unit.

FIG. 16(A) is an illustrative view showing a state in which the aerosolcontainer is exchanged from a head portion side, and FIG. 16(B) is anillustrative view showing a state in which the aerosol container isexchanged from a bottom portion side.

FIGS. 17(A) and 17(B) are illustrative views showing exampleconfigurations for opening and closing a first end portion cover portionusing a hinge and a snap lock.

FIGS. 18(A) and 18(B) are illustrative views showing exampleconfigurations for opening and closing a second end portion coverportion using only a snap lock.

FIGS. 19(A) and 19(B) are illustrative views showing exampleconfigurations in which electrical contacts are provided in theconfigurations of FIG. 18 .

DESCRIPTION OF EMBODIMENTS

The present invention will be described in detail below on the basis ofan embodiment shown in the figures.

Dimensions, materials, shapes, relative arrangements, and so on ofconstituent components described in the following embodiment are to bemodified as appropriate in accordance with the configuration of thedevice to which the invention is applied and various conditions.Therefore, the scope of the invention is not limited to the embodimentdescribed below.

FIG. 1 is a conceptual view of a discharge device for an aircraftaccording to an embodiment of the present invention.

In the figure, 1 denotes a discharge device for an aircraft, whichincludes an aerosol container 10 and discharges contents of the aerosolcontainer 10 when attached to an aircraft 100. As regards the dischargedcontents, not only a liquid but also a gas, a gas such as air, a powder,or the like may be discharged, and cases in which a sound (a horn) orthe like is discharged are also included. Sound discharge is configuredso that the sound is emitted when a gas is ejected, for example.

The discharge device 1 for an aircraft is mounted on the exterior of anairframe 101 of the aircraft 100 in a state where the aerosol container10 is housed in a sleeve 20 serving as a housing member. A dischargedrive unit 30 for discharging the contents from the aerosol container 10is built into the sleeve 20. The sleeve 20 and the aerosol container 10can be exchanged integrally, and in the following description, anassembly in which the aerosol container 10 is housed in the sleeve 20will be referred to as an aerosol container assembly 40.

The aircraft 100 is an unmanned aircraft such as a so-calledmulticopter, the airframe 101 includes a main body portion 102 and aplurality of arm portions 103 extending radially from the main bodyportion 102, and a rotary blade 104 is provided on the tip end of eacharm portion 103 via a motor 105. In the example in the figures, therotary blades 104 are shown in two locations on the left and rightsides, but as long as the rotary blade 104 is provided in a plurality,various well-known multicopters having three rotary blades (atricopter), four rotary blades (a quadcopter), six rotary blades (ahexacopter), and so on may be applied.

[Aerosol Container]

The aerosol container 10 is a container from which contents are ejectedin response to gas pressure from liquefied gas or compressed gas chargedin the interior thereof, and an existing metal aerosol can may beapplied thereto. A pressure-resistant plastic container may also beused. In the aerosol container 10, various actuators with a flow passageformed therein are attached to a stem 12 in accordance with thedischarge direction and discharge form. In the example in the figures,an actuator 14 oriented in a central axis direction is attached to thestem of the aerosol container 10. A nozzle with an orifice formedtherein may be attached to the tip end of the actuator 14, and whetherto discharge the contents in mist form or in the form of a linear jet isselected as appropriate in accordance with the discharge form anddischarge direction of the contents.

The aerosol container 10 is used horizontally, and therefore, as theform in which a propellant and the contents are sealed therein, asegregated form in which an undiluted solution is housed in an inner bagand the propellant is housed between the outer periphery of the innerbag and the inner periphery of the container main body is used. With thesegregated form, the contents can be discharged even when the attitudeof the aerosol container is in a lateral orientation (the stem ispositioned on the side) or a downward orientation (the stem ispositioned at the bottom).

The form of the propellant and the contents is not limited to thesegregated form. When the aerosol container 10 is used in an attitudewhere the stem is oriented upward during discharge, a two-phase orthree-phase container having a dip tube may be applied, and when theaerosol container 10 is used in an attitude where the stem is orienteddownward, a two-phase or three-phase container not having a dip tube maybe applied.

Note that as the propellant, a liquefied gas such as a typicalhydrocarbon (liquefied petroleum gas) (LPG), dimethyl ether (DME), or afluorinated hydrocarbon (HFO-1234ze), or a compressed gas such as carbondioxide (CO₂), nitrogen (N₂), or nitrous oxide (N₂O) may be applied, butin consideration of fire safety, a non-flammable fluorinatedhydrocarbon, carbon dioxide, nitrogen, nitrous oxide or the like ispreferable, while nitrogen is particularly preferable in considerationof the environmental load.

[Configuration of Sleeve 20]

As regards the material of the sleeve 20, the sleeve 20 is formed from astrong but lightweight material, for example a metal such as aluminum,plastic, or carbon fiber. Further, the material is not limited to a hardmaterial, and a soft material, for example a rubber material such assilicone rubber or urethane rubber, may also be used. In short, any ofvarious materials capable of holding the shape of the housing portionhousing the aerosol container 10 can be used. The term “sleeve” is usedto mean a tubular member in which the cylindrical aerosol container 10is housed.

The sleeve 20 is constituted by a cylindrical sleeve main body 21 havinga larger diameter than the aerosol container 10, a first end portioncover portion 22 covering one end portion of the sleeve main body 21,and a second end portion cover portion 23 provided on the other endportion.

The first end portion cover portion 22 is screwed to the sleeve mainbody 21 via a screw portion so as to be detachably fixed thereto, whilethe second end portion cover portion 23 is fixed to the sleeve main body21 non-detachably. Alternatively, the second end portion cover portion23 and the sleeve main body 21 may be formed integrally.

The first end portion cover portion 22 is configured to include adome-shaped cover main body 222 and a screw tube portion 223 that isscrewed to a female screw portion of the sleeve main body 21. Inconsideration of the aerodynamic characteristic, the cover main body 222has a conical or dome-shaped curved surface that gradually decreases indiameter toward the tip end and is rounded at the tip end. By formingthe cover main body 222 in a shape exhibiting a favorable aerodynamiccharacteristic in this manner, the effect of horizontal direction wind(crosswinds) can be reduced, and as a result, flight can be stabilized.

A discharge drive unit 30 is housed in the second end portion coverportion 23 positioned on a bottom portion side of the aerosol container10, and the second end portion cover portion 23 functions as a casing ofthe discharge drive unit 30. The second end portion cover portion 23 isconfigured to include a tubular portion 231 fixed at one end to a rearend portion of the sleeve main body 21 (the end portion on the bottomportion side of the aerosol container 10), and an end plate 232 thatcloses the other end of the tubular portion 231.

[Support Configurations for Aerosol Container 10 Housed in Sleeve 20]

Radial Direction Support

To support the aerosol container 10, the sleeve 20 is provided with asupport portion 21 a that holds the aerosol container 10 by means of astructure having a distance from the wall surface of the sleeve 20. Thesupport portion 21 a is provided in a plurality of locations (threelocations in the example in the figures) in an axial direction, and inthe example in the figures, the support portions 21 a hold a trunkportion 11 a of the aerosol container 10 so as to prevent movementthereof in an orthogonal direction to a central axis while allowingmovement in the axial direction. As regards the support structureprovided by the support portions 21 a, the support portions 21 a maypartially contact the trunk portion 11 a of the aerosol container 10 ina plurality of circumferential direction locations, as shown in FIG.2(A), or the support portions 21 a may support the entire circumferenceby forming an annular wall. As a method for holding the aerosolcontainer 10 in a separated state, instead of supporting the trunkportion 11 a in the above manner, the trunk portion 11 a may be set in aseparated state by supporting the two end portions, for example theshoulder portion and the bottom portion, of the aerosol container 10.

The aerosol container 10 may also be supported in a state where thetrunk portion 11 a thereof contacts the inner wall of the sleeve 20rather than being separated therefrom, but by separating the trunkportion 11 a of the aerosol container 10 from the inner wall of thesleeve 20, an insulating material or a heat storage material can beinterposed in the space formed by the separation.

Note that the sleeve 20 does not have to have a sealed structure and mayhave a partially ventilated structure. For example, a structure formedby mesh, punching, or the like may be applied. In so doing, effects suchas facilitating self-cooling during aerosol discharge by means ofoutside air and reducing the weight of the sleeve 20 can be achieved.

Axial Direction Support

As regards axial direction support of the aerosol container 10,meanwhile, a bottom portion 11 b contacts a movable plate 32 b forming apart of the discharge drive unit 30 disposed on the second end portioncover portion 23 side, while a head portion side of the aerosolcontainer 10 is held in the axial direction by bringing a flange portion14 b of the actuator 14 attached to the stem 12 into contact with apressing member 221 provided on the first end portion cover portion 22.

The pressing member 221 includes a tubular body 221 a that projects froman apex portion of the first end portion cover portion 22 toward thestem 12 in the central axis direction of the aerosol container 10, andan end portion flange portion 221 b provided on one end of the tubularbody 221 a and fixed to the first end portion cover portion 22. An axialdirection through hole is formed in the tubular body 221 a of thepressing member 221. Meanwhile, an actuator main body portion 14 a ofthe actuator 14 penetrates the pressing member 221 slidably, and a tipend surface of the tubular body 221 a either contacts or is close to theflange portion 14 b, which protrudes from the actuator main body portion14 a. The pressing member 221 may be formed integrally with the secondend portion cover portion 23.

[Configuration of Discharge Drive Unit 30]

In the example in the figures, the discharge drive unit 30 housed in thesecond end portion cover portion 23 is constituted by a cam 32 a that isdriven to rotate by a motor 31, and the driven-side movable plate 32 b,which is moved in a linear direction by the rotation of the cam 32 a.The movable plate 32 b is provided with a cam follower 32 c thatcontacts the cam 32 a, and a rotary motion of the cam 32 a is convertedinto a linear motion of the movable plate 32 b via the cam follower 32c. The movable plate 32 b is normally in a retraction limit position,whereby a valve 13 is held in a closed position. When the cam 32 a isrotated by the motor 31, the movable plate 32 b advances. Morespecifically, a contact region in which the cam follower 32 c contactsthe cam 32 a in the retraction limit position is set so that thedistance from the rotary center is short, and a contact region in whichthe cam follower 32 c contacts the cam 32 a in an advancement limitposition is set so that the distance from the rotary center is long. Inthe example in the figures, the shape of the cam 32 a is exaggerated.

[Configuration of Valve]

FIG. 2(B) shows an example of the valve of the aerosol container 10.

The stem 12 is provided with a discharge flow passage 12 a that extendsby a predetermined dimension in the axial direction from a tip endopening portion, and a stem hole 12 b that serves as a valve hole isopened in a side face of the stem 12. The stem hole 12 b is sealed by aninner peripheral surface of a gasket 13 a attached to a hole edge of athrough hole in a mounting cap 11 d.

Normally, the stem 12 is biased in a projecting direction by the gaspressure and the biasing pressure of a spring 13 b, and by pushing aninner peripheral edge of the gasket 13 a, which serves as a valve body,in the axial direction, the inner peripheral surface of the gasket 13 acomes into close contact with a hole edge of the stem hole 12 b, whichconstitutes a valve seat, whereby the valve is maintained in a closedstate.

When the movable plate 32 b is moved to the advancement limit by the cammechanism 32 of the discharge drive unit 30 described above, the aerosolcontainer 10 moves to the first end portion cover portion 22 side suchthat the flange portion 14 b of the flanged actuator 14 comes intocontact with an end surface of the pressing member 221, and as a result,the stem 12 is pressed relatively toward the inside of the container bya reaction force thereto. When the stem 12 is pressed, an innerperipheral edge of the gasket 13 a bends toward the inside of thecontainer such that the inner peripheral surface of the gasket 13 aseparates from the hole edge of the stem hole 12 b, thereby opening thevalve, and as a result, the contents pressed by the gas pressure aredischarged through the discharge flow passage 12 a in the stem 12.

The valve configuration shown in the figures is merely an example, andvarious configurations that are opened and closed by operating the stem12 may be applied as the valve configuration.

In this example, the rotary motion of the motor 31 is converted into alinear motion by a cam mechanism, but this motion conversion is notlimited to a cam mechanism, and any mechanism for converting the rotarymotion of the motor 31 into a linear motion, such as a screw feedmechanism or a rack and pinion, for example, may be applied. Further, asthe drive source, a linear motor for performing linear driving, anelectromagnetic solenoid, or the like may be used instead of a rotarymotor.

FIG. 15(A) shows an example in which a screw feed mechanism is used inthe discharge drive unit 30.

A screw feed mechanism 350 includes a screw shaft 351 fixed to themovable plate 32 b, and a rotating member 352 meshed to the screw shaft351. The screw shaft 351 extends along an extension line of the centralaxis of the aerosol container 10 and is fixed at one end to the movableplate 32 b. The rotating member 352 is fixed in the axial direction andmovable in a rotary direction, while a screw (not shown) to which thescrew of the screw shaft 351 is meshed is provided on an inner peripherythereof and teeth forming an external gear are provided on an outerperiphery thereof.

A rotary motor 310 is arranged so that a motor shaft 311 is parallelwith the screw shaft 351, and a gear 353 that meshes with the externalgear on the outer periphery of the rotating member 352 is fixed to themotor shaft 311.

When the rotating member 352 is driven by the rotary motor 310, thescrew shaft 351, which is held so as to be incapable of moving in therotary direction, moves in the axial direction, thereby moving theaerosol container 10 toward the head portion side via the movable plate32 b, and as a result, the stem 12 is pressed into the container,thereby opening the valve such that discharge can be performed. Further,when the rotating member 352 is rotated in reverse, the aerosolcontainer 10 is moved toward the bottom portion side, whereby thepressing applied to the stem 12 is released, and as a result, the valvecan be closed.

FIG. 15(B) shows an example in which a link mechanism is used in thedischarge drive unit 30.

A link mechanism 450 includes a slide shaft 451 fixed to the movableplate 32 b, a rotating member 452 that rotates about a rotary axis thatis orthogonal to the slide shaft 451, an eccentric pin 453 provided onthe rotating member 452, and a link 455 that couples the eccentric pin453 to a coupling pin 454 provided on an end portion of the slide shaft451. The slide shaft 451 is guided in a linear direction via a linearbearing 456, and the rotating member 452 is driven to rotate by a motor,not shown in the figure.

When the rotating member 452 is driven by the rotary motor, not shown inthe figure, the link 455 coupled to the eccentric pin 453 isrotationally displaced about the coupling pin 454 by the rotation of therotating member 452 such that the slide shaft 451 moves in the axialdirection via the link 455. Accordingly, the aerosol container 10 ismoved toward the head portion side via the movable plate 32 b such thatthe stem 12 is pressed into the container, and as a result, the valve isopened and discharge can be performed. Further, when the rotating member352 is rotated in reverse, the aerosol container 10 is moved toward thebottom portion side, whereby the pressing applied to the stem 12 isreleased, and as a result, the valve can be closed.

[Three Methods Used by Discharge Drive Unit]

The discharge drive unit 30 shown in FIG. 1 is an example, and any ofthree methods shown in FIG. 3 can be applied as the configuration of thedischarge drive unit 30. In FIG. 3 , the sleeve 20 is shown in asimplified square shape.

FIG. 3(A) shows a configuration in which the actuator 14 side of theaerosol container 10 is fixed to the sleeve 20, and a contact member 30Bthat contacts the bottom portion 11 b of the aerosol container 10 ispushed up by a drive unit 30A. The discharge drive unit 30 of FIG. 1 isan example of this method. In this method, the actuator 14 side isfixed, and therefore the precision of the discharge position is high.Moreover, this method can be used with aerosol containers 10 of variousdiameters.

FIG. 3(B) shows a configuration in which the aerosol container 10 isfixed to the sleeve 20 and the actuator 14 is pushed down by thedischarge drive unit 30. More specifically, the drive unit 30A of thedischarge drive unit 30 drives the contact member 30B contacting theactuator 14 in a direction for pushing the contact member 30B down.

According to this method, the mechanical mechanism can be concentratedon one side of the aerosol container 10, making the aerosol container 10compact and easy to exchange. Moreover, this method can be used withaerosol containers 10 of various heights.

Note that any mechanism that performs driving in a linear direction maybe used as the drive unit 30A in FIGS. 3(A) and 3(B), and accordingly, amotion conversion mechanism such as a cam or a screw feed mechanism thatconverts the rotary motion of a rotary motor into a linear motion can beused. Moreover, instead of a rotary motor, a linear motor for performinglinear driving, an electromagnetic solenoid, or the like may be used.

FIG. 3(C) shows a configuration in which control is performed by anexternal valve 30C instead of a valve provided in the interior of theaerosol container 10. In the figure, the external valve 30C isillustrated conceptually, but the external valve 30C can be configuredso as to be driven to open and close by a solenoid valve or the like.When the external valve 30C is used, the stem 12 of the aerosolcontainer 10 is simply connected to a pipe passage 30D, and thereforethe aerosol container 10 can be attached easily and opening/closingcontrol is also easy. When the existing aerosol container 10 is used,the stem 12 is pushed in while incorporating the aerosol container 10,for example, so that the internal valve is held in a normally openstate.

[Electrical Equipment]

A discharge control unit 210 serving as a control device for controllingthe discharge drive unit 30 is provided separately to a flight controlunit 110 for controlling flight of the aircraft 100 and provided on theairframe 101 side together with the flight control unit 110. Further, adischarge power supply 211 for driving the discharge drive unit 30 isprovided separately to a power supply for driving the aircraft 100 (thispower supply is incorporated into the flight control unit 110 and notshown in the figures) and mounted on the airframe 101 side.

Furthermore, a discharge communication unit 212 including an antenna forremotely operating the discharge drive unit 30 is provided separately toa flight communication unit 112 including an antenna for remotelyoperating the aircraft 100 and mounted on the airframe 101.

The functions of the discharge control unit 210, the dischargecommunication unit 212, and the discharge power supply 211 for thedischarge drive unit 30 may be executed partially or entirely by theflight control unit 110, the flight communication unit 112 and a flightpower supply. FIG. 2(C) shows an example in which a shared power supplyis disposed in the flight control unit 110.

[Coupling Structure for Coupling to Airframe]

Coupling portions 51, 52 that can be coupled to each other detachablyare provided respectively on the airframe 101 of the aircraft 100 andthe sleeve 20 of the aerosol container assembly 40. The couplingportions 51, 52 in FIG. 1 are illustrated conceptually, but as shown inFIG. 2(D), for example, by disposing a drive unit slide rail 51 b havinga T-shaped groove 51 a as the coupling portion 51 on the aircraft 100side and providing a housing member-side coupling portion 52 having aT-shaped fitting convex portion 52 a that is fitted to the T-shapedgroove 51 a of the slide rail 51 b on the outer periphery of the sleeve20 of the aerosol container assembly 40, the coupling portions 51, 52can be attached and detached easily. Needless to mention, the couplingportions 51, 52 are not limited to a sliding type fitting structure, anda configuration with which the coupling portions 51, 52 can be attachedand detached in a rotation direction, such as a bayonet coupling, aswell as various other coupling means facilitating attachment anddetachment, such as screwing, a clip joint, or a clamp, may be applied.

Further, as shown in FIG. 1(C), the airframe-side coupling portion 51and the housing member-side coupling portion 52 are respectivelyprovided with electrical contacts 213 a, 213 b for electricallyconnecting the discharge control unit 210 and discharge power supply 211disposed on the airframe 101 side to the motor of the discharge driveunit 30 and so on.

The electrical contacts 213 a, 213 b do not have to pass through thecoupling portions 51, 52 and may be directly connected from the sleeve20 to a connector disposed in the airframe 101 by a cable or the like,for example. Alternatively, a power supply such as a secondary batteryand a wireless communication device may be provided in the sleeve 20,and electrical signals from the flight control unit 110 disposed on theairframe 101 side may be exchanged with the flight control unit 110 inthe sleeve 20 by wireless communication.

Next, actions of the discharge device for an aircraft according to thepresent invention will be described.

[Exchange Operation]

The aerosol container assembly 40, in which the aerosol container 10 ishoused in the sleeve 20, is prepared in advance. In an exchangeoperation, the coupling portions 51, 52 are detached and the new aerosolcontainer assembly 40 is attached. By forming the coupling portions 51,52 to be easily attachable and detachable by means of a manual operationwithout the use of a tool, for example, exchange can be performedeasily. Following the exchange, the aerosol container 10 is removed fromthe sleeve 20 of the aerosol container assembly 40, and after completelydischarging the gas and contents therein, the aerosol container 10 isdiscarded. The sleeve 20 can be used repeatedly. Further, byuniversalizing the coupling portions 51, 52 that are coupled to theaircraft 100, aerosol container assemblies 40 of different sizes can beused, while the airframe 101 side of the aircraft 100 need only besubjected to minimal modification in order to provide the couplingportion 51.

Furthermore, in this embodiment, it is possible to exchange only theaerosol container 10 while keeping the sleeve 20 fixed to the aircraft100.

More specifically, as shown in FIG. 16(A), by rotating the first endportion cover portion 22 and unscrewing the screw tube portion 223, theaerosol container 10 can be removed and exchanged.

Further, as shown in FIG. 16(B), the second end portion cover portion 23may be provided with a screw tube portion 223 a and fixed detachably tothe sleeve main body 21 via a screw portion. In this case, the first endportion cover portion 22 may be fixed non-detachably to the sleeve mainbody 21. Alternatively, the first end portion cover portion 22 and thesleeve main body 21 may be formed integrally. Furthermore, in order toform an electrical connection with the discharge drive unit 30, thesleeve main body 21 may be provided with an electrical contact 213 c andthe second end portion cover portion may be provided with an electricalcontact 213 d. Thus, the second end portion cover portion 23 and thedischarge drive unit 30 housed therein can be separated from the sleevemain body 21, thereby facilitating exchange of the aerosol container 10.

In this embodiment, a screw provided on the first end portion coverportion 22 or the second end portion cover portion 23 is used to openand close the sleeve main body 21, but the sleeve main body 21 may beopened and closed using a method other than screwing. For example, acombination of a hinge and a snap lock may be used.

FIGS. 17(A) and 17(B) show an example configuration in which the firstend portion cover portion 22 is coupled to the sleeve main body 21 by ahinge 80 so as to be openable and closeable. In a closed position, thefirst end portion cover portion 22 is coupled and fixed by a snap lock70.

Various well-known configurations can be employed as the snap lock 70,but in the example in the figures, the snap lock 70 includes a lock mainbody 71 fixed to the sleeve main body 21, a lever 72 attached to thelock main body 71 to be free to rotate, a snap ring 73 attachedrotatably to a midway position on the lever 72, and a hook member 74fixed to the first end portion cover portion 22.

During coupling and fixing, the snap ring 73 is hooked onto the hookmember 74 by raising the lever 72 in a state where the first end portioncover portion 22 is closed, and by lowering the lever 72, the snap ring73 hooked onto the hook member 74 is pulled by the lever action suchthat the first end portion cover portion 22 is firmly fixed by thetension acting on the snap ring 73. When opening the first end portioncover portion 22 using the lever 72 as a fulcrum, the snap ring 73 canbe unhooked from the hook member 74 by pulling up the lever 72.

As regards the snap lock 70, the lock main body 71 may be fixed to thefirst end portion cover portion 22 and the hook member 74 may be fixedto the sleeve main body 21.

Further, FIGS. 18(A) and 18(B) show a case in which the second endportion cover portion 23 is joined by a plurality of snap locks 70 alonerather than being coupled by a hinge.

In the example in the figures, the snap locks 70 are provided in twolocations on 180° opposite sides. Likewise in this case, the second endportion cover portion 23 can be coupled to the sleeve main body 21 so asto be freely openable and closeable. When opening the second end portioncover portion 23, the levers 72, 72 of the two snap locks 70, 70 caneither be raised simultaneously or detached one at a time. In so doing,the second end portion cover portion 23 can be disconnected from thesleeve main body 21.

Likewise in this case, as shown in FIGS. 19(A) and 19(B), in order toform an electrical connection with the discharge drive unit 30, thesleeve main body 21 may be provided with the electrical contact 213 cand the second end portion cover portion 23 may be provided with theelectrical contact 213 d. In the example in the figures, the electricalcontacts 213 c, 213 d are disposed between the two snap locks 70 inpositions 90° away from the snap locks 70. Thus, the second end portioncover portion 23 and the discharge drive unit 30 housed therein can beseparated from the sleeve main body 21, thereby facilitating exchange ofthe aerosol container 10.

[Spraying Operation]

As shown in FIG. 4 , for example, during a spraying operation, theflight of the aircraft 100 is remotely operated using a steeringterminal 120 and the discharge device 1 is remotely operated using adischarge operation terminal 160. The discharge operation terminal 160is provided with a discharge button 163 and a stop button 164, and whenan operator presses the discharge button 163 while viewing an image on adisplay 165, a discharge command signal is transmitted and received inthe discharge communication unit 212 installed in the aircraft 100. Thedischarge drive unit 30 is then driven by the discharge control unit210, whereby the stem 12 of the aerosol container 10 is pressed in, andas a result, the contents are discharged. When the stop button 164 ispressed, a stop command signal is transmitted, causing the dischargedrive unit 30 to release the pressing applied to the stem 12, and as aresult, the discharge is stopped.

Switching between discharge and stopping can be performed not only byoperating the buttons but also automatically in accordance with aprogram stored in advance. For example, a route can be pre-programmed,the position on a map and the height can be detected using a signal froma GPS and an altimeter, respectively, discharge can be started when apredetermined position is reached, and discharge can be stopped whendischarge over a predetermined area is complete.

[Example in which Extension Tube is Provided]

FIG. 5 shows an example configuration in which a nozzle 15 of theaerosol container is connected via an extension tube 16.

In this example, the aerosol container assembly 40 is mounted on thelower surface of the airframe 101, the nozzle 15 is attached to a tipend position of an arm portion of the airframe 101, and the nozzle 15 isconnected to the aerosol container 10 in the aerosol container assembly40 via the flexible extension tube 16.

Thus, the nozzle 15 can be disposed in a position away from the mountingposition of the aerosol container assembly 40, whereby the dischargeposition can be set freely and the layout freedom can be improved. Forexample, by attaching the nozzle 15 to a gimbal, it becomes easy tomanipulate the discharge direction remotely.

As shown in FIG. 5(B), the nozzle 15, the extension tube 16, and theaerosol container 10 are formed to be disposable as an integrated unit.

The discharge device for an aircraft according to the present inventionis particularly effective in pesticide spraying.

A conventional unmanned aircraft for spraying pesticides or the like hasa tank, and therefore a person must transfer the pesticides to the tank.Not only is the transfer operation laborious, but it is also necessaryto clean a pipe system, and moreover, the work of transferring harmfulchemicals is dangerous to the body of the user. Hence, a conventionalunmanned aircraft is not suitable for use by the elderly or the like.

When the aerosol container assembly 40 of the present invention is used,the aerosol container assembly 40 can easily be attached to and detachedfrom the airframe 101, which is preferable in terms of safety. Moreover,by exchanging the extension tube 16 integrally with the aerosolcontainer 10, the discharge device can be used without the need toconsider cleaning and maintaining a pipe system.

MODIFIED EXAMPLES

Next, various modified example of the discharge device for an aircraftaccording to the first embodiment will be described. In the followingdescription, mainly only points that differ from the above embodimentwill be described. Identical constituent parts have been allocatedidentical reference symbols, and description thereof has been omitted.

The modified examples differ in terms of configuration from thefollowing four viewpoints.

Viewpoint 1: the coupling portions between the sleeve 20 and theairframe 101.

Viewpoint 2: the position of the discharge drive unit 30.

Viewpoint 3: exchange of the aerosol container 10.

Viewpoint 4: the positions of the discharge control unit 210, thedischarge communication unit 212, and the discharge power supply 211(referred to as a whole as the electrical equipment).

In the embodiment described above, the sleeve 20 is coupled detachablyto the airframe 101 (viewpoint 1), the discharge drive unit 30 is on thesleeve 20 side (viewpoint 2), the aerosol container 10 is exchangeablerelative to the sleeve 20 (viewpoint 3), and the electrical equipment ison the airframe 101 side (viewpoint 4).

Note that the term “exchangeable” in viewpoint 3 expresses a state ofbeing exchangeable using a method presented to the user by themanufacturer, while “non-exchangeable” expresses a state in which themanufacturer has not presented an exchange method to the user.

Respective modified examples will be described below from these fourviewpoints.

Modified Example 1

FIG. 6 shows modified example 1.

Modified example 1 is identical to the first embodiment in that thesleeve 20 is coupled detachably to the airframe 101 (viewpoint 1), thedischarge drive unit 30 is on the sleeve 20 side (viewpoint 2), and theaerosol container 10 is exchangeable relative to the sleeve 20(viewpoint 3).

Modified example 1 differs from the first embodiment in that theelectrical equipment is positioned on the sleeve 20 side (viewpoint 4).

More specifically, the discharge control unit 210, the dischargecommunication unit 212, and the discharge power supply 211 are housed inthe second end portion cover portion 23 housing the discharge drive unit30.

By incorporating the discharge control unit 210, the dischargecommunication unit 212, and the discharge power supply 211 into thesleeve 20 side, electrical contacts with the airframe 101 are notrequired.

Modified Example 2

FIG. 7 shows modified example 2.

Modified example 2 is identical to the first embodiment in that thesleeve 20 is coupled detachably to the airframe 101 (viewpoint 1), thedischarge drive unit 30 is on the sleeve 20 side (viewpoint 2), and theelectrical equipment is on the airframe 101 side (viewpoint 4), but interms of viewpoint 3, modified example 2 differs from the firstembodiment in that the aerosol container is non-exchangeable.

More specifically, the first end portion cover portion 22 of the sleeve20 is fixed integrally to the sleeve main body 21.

With this configuration, the aerosol container is non-exchangeable, andtherefore, each time the aerosol container is used up, almost the entiredevice, including the discharge drive unit, is exchanged. Thus, a highdegree of reliability is achieved.

Modified Example 3

FIG. 8 shows modified example 3.

Modified example 3 is identical to the first embodiment in that thesleeve 20 is coupled detachably to the airframe 101 (viewpoint 1) andthe discharge drive unit 30 is on the sleeve 20 side (viewpoint 2) butdiffers from the first embodiment in that the aerosol container 10 isnon-exchangeable, similarly to modified example 2 (viewpoint 3), and thedischarge control unit 210, the discharge communication unit 220, andthe discharge power supply 211 are positioned on the sleeve 20 side(viewpoint 4).

In the aerosol container assembly 40 having this configuration, allconfigurations, including the aerosol container 10, the discharge driveunit 30, and the electrical equipment, are incorporated into the sleeve20, and therefore the aerosol container assembly 40 simply has to bemounted on the airframe 101. This is effective in cases where theaircraft cannot be modified, such as when the aircraft is rented out.

Modified Example 4

FIG. 9 shows modified example 4.

Modified example 4 is identical to the first embodiment from viewpoint3, the aerosol container 10 being exchangeable relative to the sleeve20, and from viewpoint 4, the electrical equipment being positioned onthe airframe 101 side, but differs from the first embodiment fromviewpoint 2, the discharge drive unit 30 being positioned on theairframe 101 side, and viewpoint 1, the sleeve 20 being coupled to thedischarge drive unit 30 rather than to the airframe 101.

In the case of modified example 4, the sleeve 20 does not include thesecond end portion cover portion 23 of the first embodiment, and acasing 35 of the discharge drive unit 30 is fixed to the airframe 101.The casing 35 is basically shaped identically to the second end portioncover portion 23 of the first embodiment.

The sleeve 20 is provided with a fitting tube portion 251 serving as asleeve-side coupling portion for coupling the sleeve 20 to the casing 35of the discharge drive unit 30, and the casing 35 is provided with afitting reception portion 252 serving as a casing-side coupling portion.Needless to mention, the coupling structure may be any detachablestructure, and a screw engagement may also be employed.

By fixing the casing 35 of the discharge drive unit 30 integrally to theairframe 101 in this manner, there is no need to provide electricalcontacts, meaning that electrical connection defects can be avoided, andas a result, the reliability improves.

Further, there is no need to house the discharge drive unit 30 on thesleeve 20 side, and therefore a cost reduction effect is acquired inrelation to the sleeve 20 itself.

Modified Example 5

FIG. 10 shows modified example 5.

Modified example 5 is identical to the first embodiment from viewpoint4, the electrical equipment being positioned on the airframe 101 side,but differs from the first embodiment from viewpoint 3, the aerosolcontainer 10 being non-exchangeable, viewpoint 2, the discharge driveunit 30 being positioned on the airframe 101 side, and viewpoint 1, thesleeve 20 being coupled to the discharge drive unit 30 rather than tothe airframe 101.

Likewise in the case of modified example 5, similarly to modifiedexample 4, the sleeve 20 does not include the second end portion coverportion 23, and the casing 35 of the discharge drive unit 30 is fixed tothe airframe 101. The sleeve 20 is provided with the fitting tubeportion 251 serving as the sleeve-side coupling portion for coupling thesleeve 20 to the casing 35 of the discharge drive unit 30, and thecasing 35 is provided with the fitting reception portion 252 serving asthe casing-side coupling portion.

By fixing the casing 35 of the discharge drive unit 30 integrally to theairframe 101 in this manner, there is no need to provide electricalcontacts, meaning that electrical connection defects can be avoided, andas a result, the reliability improves. Moreover, there is no need tohouse the discharge drive unit 30 on the sleeve 20 side, and therefore acost reduction effect is acquired in relation to the sleeve 20 itself.

Modified Example 6

FIG. 11 shows modified example 6.

Modified example 6 is identical to the first embodiment from viewpoint2, the discharge drive unit 30 being fixed integrally on the sleeve 20side, viewpoint 4, the electrical equipment being positioned on theairframe 101 side, and viewpoint 3, the aerosol container 10 beingexchangeable, but differs from the first embodiment from viewpoint 1,i.e., the coupling between the sleeve 20 and the airframe 101, thesleeve 20 being fixed non-detachably to the airframe 101.

Modified example 6 is effective in a case where the aerosol containers10 that can be used are limited. Since it is only necessary to fix thesleeve 20 and the discharge drive unit 30 to the airframe 101, open thefirst end portion cover portion 22, and exchange the aerosol container10 housed in the sleeve 20, a cost advantage is acquired.

Note that fixing of the discharge drive unit 30 to the airframe 101 inmodified examples 4 and 5 or fixing of the sleeve 20 to the airframe 101in modified example 6 is realized by screw fastening using a bolt or thelike, fixing using a band, fixing by adhesion, and so on. Alternatively,the fixing subject components may be manufactured integrally with theairframe 101.

[Various Examples of Mounting the Aerosol Container Assembly on theAircraft]

In the examples of the first embodiment and the first to sixth modifiedexamples, cases in which the aerosol container assembly 40 is mountedsingly were described, but a plurality of aerosol container assemblies40 may be mounted. For example, FIG. 12(A) shows an example in which twoaerosol container assemblies 40 are provided on the lower surface of theairframe. In this example, the coupling portions 51, 52 are provided foreach of the aerosol container assemblies 40, but shared couplingportions may be provided, and coupling portions 51, 52 of preferredshapes are disposed in accordance with the layout of the aerosolcontainer assemblies 40.

Further, the aerosol container assembly 40 is mounted with the aerosolcontainer 10 in a horizontally oriented state, but the orientation ofthe aerosol container 10 may be set as desired, and by modifying thecoupling portions 51, 52, the aerosol container 10 can be mounted in adesired orientation. For example, as shown in FIG. 12(B), by providingcoupling portions 51, 52 that extend vertically downward from the lowersurface of the airframe 101, the aerosol container 10 can be attached ina state where a center line thereof (a center line of the trunk portion)is oriented in a vertical direction. Thus, simply by exchanging thecoupling portions 51, 52, the mounting layout of the aerosol containerassembly 40 can be set freely. In this example, the nozzle is on theupper end such that discharge is performed sideward, but as shown inFIG. 12(C), discharge may also be performed downward.

[Various Layouts of the Aerosol Container Assembly]

Next, referring to FIGS. 13 and 14 , various mounting layouts of theaerosol container assembly 40 will be described.

FIG. 13(A) shows an example in which the aerosol container assembly 40is mounted on the lower surface of the airframe 101 and arranged inparallel with a mounted camera 106. A center of gravity position can beset in the center in accordance with the weight balance between theaerosol container assembly 40 and the camera 106, and thus the aerosolcontainer assembly 40 can be disposed with stability.

FIG. 13(B) shows an example in which a plurality of aerosol containerassemblies 40 are arranged on the upper surface of the airframe 101.

In so doing, the operation to exchange the aerosol container assembly 40can be performed easily. Further, advantages are gained in that landingof the airframe 101 is not impaired and the field of view of the camera106 suspended from the lower surface is also not impaired.

FIG. 13(C) shows an example in which two aerosol container assemblies 40are attached to side portions (the left and right sides in the figure)of the airframe 101.

Thus, advantages are gained in that landing is not impaired, exchangecan be performed easily, and the airframe 101 can be stabilized andthereby less likely to be affected by crosswinds.

In FIG. 14(A), the aerosol container assembly 40 is mounted on a legportion 107 of the airframe 101 via an arm 60.

In FIG. 14(B), the aerosol container assembly 40 is disposed in aposition a predetermined distance above the upper surface of theairframe 101 via the arm 60.

In FIG. 14(C), the aerosol container assembly 40 is disposed in aposition a predetermined distance below the lower surface of theairframe 101 via the arm 60.

By employing these arrangements, effects are acquired in that downwashfrom the rotary blades 104 can be avoided, distance can be securedbetween the aircraft 100 and a target, the risk of a collision and theoccurrence of turbulence can be suppressed, the contents can bedischarged into spaces that the aircraft 100 cannot enter, and so on.

Note that in the embodiment and various modified examples describedabove, examples in which a multicopter is used as the unmanned aircraftwere described, but the aircraft may also be a fixed-wing aircraft, arotorcraft, an air balloon, a glider, or the like.

REFERENCE SIGNS LIST

-   -   1 Discharge device    -   10 Aerosol container    -   11 Container main body    -   11 a Trunk portion    -   11 b Bottom portion    -   11 d Mounting cap    -   12 Stem    -   12 a Discharge flow passage    -   12 b Stem hole    -   13 Valve    -   13 a Gasket    -   13 b Spring    -   14 Flanged actuator    -   14 a Actuator main body portion    -   14 b Flange portion    -   15 Nozzle    -   16 Extension tube    -   20 Sleeve (housing member)    -   21 Sleeve main body    -   21 a Support portion    -   22 First end portion cover portion    -   221 Pressing member    -   221 a Tubular body    -   221 b End portion flange portion    -   222 Cover main body    -   223 Screw tube portion    -   23 Second end portion cover portion    -   231 Tubular portion    -   232 End plate    -   30 Discharge drive unit    -   31 Motor    -   32 a Cam    -   32 b Movable plate    -   32 c Cam follower    -   40 Aerosol container assembly    -   51 Airframe-side coupling portion    -   51 a T-shaped groove    -   51 b Slide rail    -   52 Housing member-side coupling portion    -   52 a Fitting convex portion    -   60 Arm

FIGS. 1(F) to 1(K)

-   -   70 Snap lock    -   71 Lock main body    -   72 Lever    -   73 Snap ring    -   74 Hook member    -   80 Hinge

FIG. 15

-   -   350 Screw feed mechanism    -   351 Screw shaft    -   352 Rotating member    -   353 Gear    -   450 Link mechanism    -   451 Slide shaft    -   452 Rotating member    -   453 Eccentric pin    -   454 Coupling pin    -   455 Link    -   456 Linear bearing

The invention claimed is:
 1. A discharge device for an aircraft, towhich an aerosol container can be attached, and which dischargescontents of the aerosol container when attached to the aircraft, whereinthe discharge device is mounted on an airframe of the aircraft in astate where the aerosol container is housed inside a housing member,wherein: a discharge drive unit is provided to discharge the contentsfrom the aerosol container, the housing member comprises a housingmember main body in which the aerosol container is housed, and a lidbody for opening and closing an opening portion provided in the housingmember main body, and the aerosol container can be exchanged by openingthe lid body in a state where the housing member main body is attachedto the airframe, the lid body includes the discharge drive unit and isconfigured to be detached from the housing member main body togetherwith the discharge drive unit, and the main body is provided with anelectrical contact.
 2. The discharge device for an aircraft according toclaim 1, wherein the discharge drive unit is configured to discharge thecontents by moving a container main body of the aerosol container sothat a stem projecting from the container main body is pressed into thecontainer main body.
 3. The discharge device for an aircraft accordingto claim 1, wherein the discharge drive unit is provided in the housingmember.
 4. The discharge device for an aircraft according to claim 1,wherein the discharge drive unit is provided on an airframe side.
 5. Thedischarge device for an aircraft according to claim 1, furthercomprising a control device for controlling the discharge drive unit. 6.The discharge device for an aircraft according to claim 5, furthercomprising a communication device for operating the discharge drive unitremotely.
 7. The discharge device for an aircraft according to claim 5,further comprising a power supply for driving the discharge drive unit.8. The discharge device for an aircraft according to claim 1, whereinthe discharge drive unit discharges the contents by fixing a containermain body of the aerosol container, among a stem that projects from thecontainer main body and the container main body, and pressing the steminto the container main body.
 9. The discharge device for an aircraftaccording to claim 1, wherein the housing member and the airframe areprovided with coupling portions that are coupled to each other.
 10. Thedischarge device for an aircraft according to claim 1, wherein thehousing member main body is formed in a tubular shape extending in acentral axis direction of the aerosol container, and the opening portionand the lid body are provided on a head portion side and/or a bottomportion side of the aerosol container.
 11. The discharge device for anaircraft according to claim 10, wherein the opening portion and the lidbody are provided on the head portion side of the aerosol container, andthe housing member is configured so as to open on the head portion sideof the aerosol container.
 12. The discharge device for an aircraftaccording to claim 10, wherein the opening portion and the lid body areprovided on the bottom portion side of the aerosol container, and thehousing member is configured so as to open on the bottom portion side ofthe aerosol container.
 13. The discharge device for an aircraftaccording to claim 1, wherein the lid body is configured to be screwedto the housing member main body.
 14. The discharge device for anaircraft according to claim 1, wherein the lid body comprises fixingmeans supported to be capable of rotating relative to the housing membermain body via a hinge and that couples and fixes the lid body in aclosed position.
 15. The discharge device for an aircraft according toclaim 1, wherein the housing member comprises a support portion thatholds the aerosol container by means of a structure having a distancefrom a wall surface of the housing member.
 16. The discharge device foran aircraft according to claim 1, wherein the lid body is provided withan electrical contact.